Wing structure for aircraft



Dec. 22, 1942. c. DORNIER WINGASTRUCTURE FOR AIRCRAFT 3 Sheets-Sheet 2 Filed March 20, 1959 INVENTOR. CLA UDE DOR/WER.

Dec. 22, 1942. C, `DQRmL-:R 2,306,015

WING STRUCTURE FOR AIRCRAFT Filed March 20, 1939 3 Sheets-Sheet .3

CLA UDEDO R/v/EQ.

ATTORNEY.

Patented Dec. 22, 1942 WING STRUCTURE Foa AIRCRAFT Claude see, Germany; Custodian Dornier, Friedrichshafen-on-the-Bodenvested in the Alien Property Application March 20, 1939, Serial No. 262,848 y, In Germany March 25, 1938 8 Claims.

The-present invention relates to an aircraft wing structure having a so-called rolling wing, i. e. an additional vwing which, under normal ying conditions, is embedded' in a stationary wing and which can be protracted, for example for taking` off or landing purposes.

An object of the present invention is the provision of awing structure of the type set forth in which the additional wing is movable in the direction of flight and which is connected with a stationary Wing and with the fuselage of the aircraft. l

The additional orauxliarywing lits into the underside of the main wing so that it supplements the profileof the main wing when in position for high speed yng. The auxiliaryl wing rests also in a guide provided in the fuselage or the outside thereof and is movable in said guide inthe direction of flight. With the structure according to the present invention the major part of the forces due to the air pressure are absorbed by said guide. In order to prevent fluttering the auxiliary wing is also connected in a more or less conventional manner vwith the main wing by means of one or a plurality of rigid or movable stays or connectingv members which, however, in the structure according to the present invention take up only a small part of the forces acting on the' wing. The

' auxiliary wings may also extend through and be supported by the motor gondolas which are connected with the main wing. In such manner use can be made of the rearward extension of said gondolaslwhich extension is provided for aerodynamic reasons but is otherwise `not used.

In a preferred embodiment of the present invention connecting members are completely eliminated and the free carrying principle is fully materialized; in such an embodiment the support guide, of course, must be made stronger. Greater stability can be obtained by interconnecting the spars of the individual auxiliary wings and extending said spars. through the fuselaged or a suitable extension thereof. Such a. construction is particularly vsuitable for high Wing and low wing airplanes because in such planes the spars of the auxiliary wings can be located above or below the fuselage and do not interfere with the construction of the interior of the fuselage. The guides for the auxiliary wings may be curved; It is simpler, however, and less expensive to make the guides straight and swingable about their forward ends. For lowering the auxiliary wings the guides are then first swung downward and, then the auxiliary wings are moved rearward along the guides,

, of a motor gondola of an airplane according toA Further and other objects of the present invention will be hereinafter set forth in tlieiaccompanying specification and shown in the 'drawings which,`by wayof illustration, show what I now consider to be a preferred embodiment of my invention.

Y In the drawings:

Figure 1 is a diagrammatic part sectional view Vof a'wing structure' according to the present invention.

Figure 2 is adiagrainmatic sectional view of Figure 3 is a sectional view taken along line` 3-3 in Fig. 1.

Figure l is a diagrammatic part sectional view of a lateral wing plane according to the present invention.

Figure 5 is a' diagrammatic part sectional view of a high wing plane according to the present invention.

Figure 6 is a diagrammatic part sectional view the present invention.`

Figure 7 is adiagrammatic top view of an airplane according to the present invention.

Figure 8 is a diagrammatic side view of a modiy fied airplane with parts breken away and according to the present invention.

Figure 9 is an isometric bottom View of the airplane, shown in Fig. 8.

Like parts are designated by like numerals in all figures of the drawings.

Referring more particularly to Fig. l of the drawings numeral I designates a normal stationary main wing which is cut through adjacent to its root so that the slot hole guide 2 is visible which is rigidly connected with the outside of Lthe fuselage I". In. the guide'Z slides the slide member or link block 3 to which a retractable auxiliary wing 4 is rigidly connected. W hen lowered the auxiliary Wing assumes the position 4 which is shown Ain dash and 'dotted lines.

` Figure 2 shows a section through the stationary main wing and through the movable auxiliary wing the sectionv being taken. near the outer end of Ithe latter. One end of a stay orv connecting member 6 is pivoted at 5 to the auxiliary wing 4. The other end of said stay is provided with a slide member y1 which slides in guide which is built into the main wing' i. The positions of the movable parts when the auxiliary wing is lowered are shown in dash and dotted lines, stay t being in position 6, fulcrum `5 in position 5 and wing in position t'.

Figure 3 is a section taken along line I-l in Fig. 1 and shows the support of the auxiliary wing. Spar 3 of wing 4 is rigidly connected with the slide member 3. Guide 2 is rigidly connected by means of rivets, bolts or the like with the exterior wall I of thefuselage and forms together with member 3 a `cantilever support f or auxiliary wingl.

Figure 4 shows the application of the present invention to a lateral wing plane whereby the guides simply consist of reinforcements I2 on the lateral wall of the fuselage and the spar I I of the auxiliary wings extends through the fuselage.

Figure 5 shows the application of the present invention to a high wing plane. In thiscase a continuous auxiliary wing 4 can be used because the .Wing does not interfere with the interior construction of the fuselage.

Figures 6 and?? show the arrangement of guides 2 in the extension of a motor gondola or nacelle as well as in the fuselage I'. These figures are self-explanatory.

Figures 8 and 9 lshow the applicationof the present invention toa low wing plane...-` Straight guide members 2 are used in'this embodiment of the invention; The foreends of ithe members 2" are hinged at I3 to the fuselage and can be swung downward by means of a mechanism conasoaoio 3. In an aircraft having a fuselage, an aerofoil including a cambered main wing consisting of a main portion and a trailing portion, and an auxiliary wing adapted to be'faired under the trailing portion of said main wing and to be projected rearwardly and downwardly in parallel relation to said main wing, connecting means provided at the end of said auxiliary wing adjacent to said fuselagalsupport' means swingably connected with `said fuselage and adapted to swing about an axis substantially parallel to the longitudinal axis of said aerofoil and movably connected with said connecting means and cantileverlike supporting said auxiliary wing.

4. In an aircraft having a fuselage, an aerofo'il including acambered main wing consisting of a main portion and a trailing portion, and an auxiliary wing' adapted to be faired under the p0rti0n'ofvsiid min wml and i0 be sisting of a threaded spindle I6 'having av hand wheel I4 and being swingably connected withthe guide member 2" by means of a pivot I5. Spindle I6 extends throughput member I1 whichis rotatably connected with the fuselage. Figure 9 is a bottom view of an airplane as per Fig. 8 whereby the rolling or auxiliary wings 4 are lowered suspending' staysn along the lowered guides 2".'

6 are provided of the type shown in Fig. 2. Be-

tween the swingable slot hold guide means 2" vany auxiliary wing portion is provided which is adapted to be faired under the fuselage to form a continuous undersurface thereof when in rey tracted position.

AWhile I believe the above described embodiments of my invention to be ,preferred embodiments, I wish it to bev understoodv that-I do not, desire to be limited to the exact details of design and construction shown and described, for obvi-l ous modifications occur the art. I claim:

l. In an laircraft having a fuselage,-anaerofoil` including a'cambered main wing consistingof a main portion'and a'trailing portion, and an auxiliary wing adapted toj,` befairedunder the trailing portion of saidmain wing andv tobe. projected rearwardly and downwardly in parallel relationto said main wing, connecting means provided at the end of saidauxiliary wing adjacent to said fuselage, support means provided in said fuselage and movably connected with said connecting means and forming therewitha cantilever support for said auxiliary wing.

2. In-an aircraft having a fuselage, an aerofo including a cambered main'wing consisting of a main lportion and a trailing portion. and an auxiliary. wing adapted to be faired undery the trailing portion -of said 'main wing and to be 'projected'rearwardly and downwardly in parallel relation to said main wing, link-block means provided at the end of said auxiliary wing adjacent tok said fuselage, support means provided in said fuselage and comprising-a slot hole slidingly accommodating said link block means andforming therewith a cantilever support for said auxiliary wing. I l f to a person projected rearwardly and downwardly in parallel 4relation to said main wing, link-block means provided at the end of said auxiliary wing adjacent to said fuselage, support means'swingably connectedwith said fuselage andfcomprising a slot hole slidingly accommodatingsaid link block means and cantileverlike supporting said auxily isrywing. i v

5. In anaircraft having a fuselage,two aero.

foils each Aincluding a cambered main wing consisting of a main portionrand'a trailing portion, l

two auxiliary lwings adaptedto be faired. individuallyunder the trailing portions of said main wings and to be projected rearwardly and downwardly in parallel relation to said wing. connecting means rigidlyconnected to and interconnectconnected with said other connecting means and.

forming' therewith a, cantilever support for said auxiliarywingsyu: '8. In an aircraft-havinga fuselage, two aeroy foils each including a 'cambered'main wing con- 5y/'sisting 'of amain portionland a trailing portion. f two 'auxiliary 'wings adapted tof-be faired-indi4 viduallyunder thetrailing-portions of said main iwings and to be projectedrearwardlyand'down- -wardly invparallel relation to said wing, connect- `ing means rigidly connected to and'intereonnecting said auxiliary wings. slide means rigidly' con'- nected withsaid-'connecting-means adjacent to said'fuselage, and support means provided on said fuselage and slidinglyy connected with said `slide means and forming therewith a cantilever foils each including a cambered main wing conf sisting of a main'portion and a trailing portion,

two auxiliary wings adapted tovbe faired indi-V vidually under the trailing portions of said main v wings and to'be projected rearwardly and downwardlyA in parallel relation to said wi portion and a trailing portion, and auxiliary wings adapted to be faired individually under the trailing portions of said main wings and to bey projected rearwardly and downwardly in parallel relation to said main wings, each of said auxiliary wings having a root portion, connecting means provided at said root portions, support',v means swingably connected with said fuselage and adapted to swing about an axis parallel to the longitudinal axis of said aerooil and movably connected with said connecting means and cantileverlike supporting said auxiliary wing, and an auxiliary wing portion rigidly connectedwith said auxiliary wings and disposed between said support means and adaptedv to be faired under said fuselage.

CLAUDE DORN'IER. 

